N325QS
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NETJETS AVIATION, INC. (DXTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
VARIOUS CABIN FLOOR EMERGENCY LIGHTS FAIL TO ILLUMINATE. THE RED EMERGENCY EXIT FLOOR LIGHT, ADJACENT WHITE FLOOR LIGHT, DO NOT ILLUMINATE. THE LAV EMERGENCY FLOOR LIGHT IS VERY DIM/OBSCURED. THERE IS AN INCORRECT RED FLOOR LIGHT AT CLUB SEATING AREA, THIS SHOULD BE WHITE. THERE IS NO RED EMERGENCY FLOOR LIGHT AT THE MAIN ENTRY DOOR, IT IS WHITE INSTEAD. CORRECTIVE ACTION: REMOVED AFT DIM EMERGENCY FLOORLIGHT P/N 0434LS00-01 NSN AND INSTALLED NEW CUSTOMER SUPPLIED LIGHT P/N 0434LS00-01 NSN. FOUND FAULTY MID EMERGENCY LIGHT, REMOVED EMERGENCY LIGHT P/N 0434LS00-01 NSN AND INSTALLED NEW CUSTOMER SUPPLIED LIGHT 0434LS00-01 NSN. RESTORED ALL FLOOR LIGHT TO THE ORIGINAL CONFIGURATION. OPS CHECK GOOD. ALL WORK DONE IN REFERNCE TO EMBRAER PHENOM AMM 33-52-00
CENTRAL DISPLAY SYSTEMS: CRUISING AT FL410 RECEIVED MULTIPLE CAS MESSAGES AS FOLLOWS. PRESN AUTO FAIL, SWPS FAULT, AMS CTRL FAIL, AP FAIL, YD FAIL. THE FOLLOWING WHITE ADVISORY MESSAGES ALSO DISPLAYED. STBY BARO NOCOMP, GSD 1 FAIL, SWPS ICE SPEED, HSDB FAULT. LEFT MAIN GEAR INDICATION WAS NOT INDICATING UP AS PART OF FAILURE. PERFORMED EMERGENCY GEAR EXTENSION WHEN LEFT MAIN DID NOT INDICATE DOWN AND LOCKED. AFTER LANDING ADS 1 HTR FAIL CAS MESSAGE ALSO APPEARED. CORRECTIVE ACTION; REPLACED GSD 1 IAW PHENOM 300 AMM 31-41-01.COMPLIED WITH DATA CONCENTRATOR UNIT SOFTWARE/CONFIGURATION UPLOAD IAW PHENOM 300 31-41-01 OPS CHECK GOOD
CABIN EMERG LIGHT: DURING FLIGHT CONTINUOUS FLASHING OF CABIN EMERGENCY FLOOR AND DOOR EXIT AND CABIN LIGHTS. WITH SWITCHES EITHER IN ARMED OR ON POSITION. VIDEO TO FOLLOW. CORRECTIVE ACTION: REMOVED AND REPLACED #1 AND #2 EMERGENCY BATTERIES IAW EMBRAER PHENOM 300 A.M.M. 33-52-01. REMOVED #1 P/N 640-13595-00 S/N 006343 INSTALLED P/N 640-13595-00 S/N 005711 REMOVED #2 P/N 640-13595-00 S/N 006342 INSTALLED #2 P/N 640-13595-00 S/N 005861.
EMERGENCY LIGHTS IN THE "ARM" POSITION, EMERGENCY LIGHTS WERE FLASHING AND DRAINED BOTH EMERGENCY BATTERIES. REMOVED AND REPLACED #1 AND #2 EMERGENCY LIGHT POWER UNIT.
DURING MXC NOTED FWD EXTERIOR EMERGENCY LIGHT RETAINING WATER AND SEVERAL LEDS INOP
FLOOR EMERG EXIT LIGHT: EMERGENCY FLOOR EXIT LIGHT BELOW SEAT 3 IS OUT OF RECESS AND HANGING IN AISLE BY WIRE. INSERTED AND RESECURED EMERGENCY FIOOR EXIT LIGHT BELOW SEAT 3 SOCKET IAW EMB505 SPM 20·00-00. OPS/CK GOOD, TO CONTINUE
FLOOR EMERG EXIT LIGHT: FLOOR EMERGENCY EXIT LIGHT BELOW SEAT ONE HAS BEEN PULLED OUT OF ITS RECESS AND IS HANGING IN AISLE BY WIRE. REINSTALLED FLOOR EMERGENCY EXIT LIGHT IN THE FLOOR PATH BELOW SEAT ONE IAW EMB-505 AMM 33-52-11, EMERGENCY LIGHT OPERATIONAL CHECK SATISFACTORY.
EMER LIGHTS FLASHING ENROUTE WITH SWITCH IN ARM POSITION. NOW ON STEADY IN ARM POSITION. BEGAN TROUBLESHOOTING, FOLLOWING FIM TASK 33·50·00·810·802-A SETTED EMER LT SWITCH TO THE ARM POSTION, LIGHTS DID NOT FLICKER, LIGHTS CAME ON WITH SWITCH IN ARM POSITION FOR MORE THAN MIN. GAINED ACCESS TO #2 EMER BATTERY, DISCONNECTED CONNECTOR P1360 FROM BATTERY, PLACED SWITCH ON ARM POSTION & LIGHTS DID NOT COME ON. REMOVED AND INSTALLED THE BATTERY IAW AMM 33-52-01. PERFORMED OPS CHECK WITH SAME RESULT, CONTINUED WITH FIM & GAINED ACCESS TO 1# EMER BATTERY. REMOVED #1 AND INSTALLED THE BATTERY IAW AMM 33·52-01, OPS CHECKED GOOD, AIRCRAFT OK TO RETURN TO SERVICE,
MAIN DOOR: THERE IS A LOOSE SCREW PROTUDING UP ABOUT AN INCH THAT IS CREATING A TRIPPING HAZARD ON THE LEFT CORNER OF THE FIRST STEP ON THE MAIN CABIN ENTRY DOOR. //SIGNOFF// SECURED LOOSE SCREW ON MCD STEP IAW EMB PHENOM 300 MM 52-14-00
CORROSION UNDER STATIC WICK BASE ON RH WINGLET TRAILING EDGE CAUSED STATIC WICK BASE TO FALL OFF. CORROSION REMOVAL WAS OUTSIDE OF SRM LIMITS. PERFORMED AN EXTERNAL DOUBLER PATCH AROUND THE TRAILING EDGE (TACO PATCH).
UPPER LEFT CAM LOCK CLOSED INDICATOR DOESN'T SHOW ANY GREEN THROUGH THE WINDOW. INSPECTED UPPER LEFT CAM LOCK CLOSED INDICATOR, REMOVED STEPS AND CLEANED EXCESS GREASE FROM INDICATOR AND REINSTALLED STEPS, VERIFIED PROPER OPERATION AND INDICATION IAW AMM 52-11-00-200-801.
EMERG LIGHT SWITCH: SWITCH ON THE ARM POSITION DURING FLIGHT ALL EMERGENCY LIGHT CAME ON AND STARTED FLICKERING .PUT SWITCH OFF POSITION BACK TO ARM POSITION AND ALL EMERGENCY LIGHT WERE ON AND FLICKERING AT INTERVAL. // SIGNOFF // REMOVED FAULTY AFT EMERGENCY LIGHTS BATTERY AND REPLACED WITH A NEW CUSTOMER SHIPPED EMERGENCY BATTERY. PERFOR1V1ED A SATISFACTORY OPERATIONAL CHECK OF THE EMERGENCY LIGHT SYSTEM WITH NO DEFECTS NOTED. CLOSED ALL ACCESS GAINED TO FACILITATE THE MAINTENACE, AIRCRAFT INTERIOR RETURN TO ITS ORIGINAL CONFIGURATION. ALL WORK DONE IN REFERENCE WITH EMB-505S AMM 33-52-00.
DURING ACCOMPLISHMENT OF EMBRAER SERVICE BULLETIN 505-55-0004 REV 01 (DATED 06/24/2020) WE NOTED THE FOLLOWING MASS BALANCE WEIGHTS BELOW TOLERANCE AT LEFT ELEVATOR: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (13 EACH BELOW MINIMUM OF 84G), HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G), MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-615 AS PER SERVICE BULLETIN INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RIGHT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (14 EACH BELOW MINIMUM OF 84G), HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G), MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-616 AS PER SERVICE BULLETIN INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATORâS GMM REQUIREMENTS.
PASSENGER DOOR HANDLE BROKE OFF WHILST OPENING THE DOOR. SIGN OFF. REMOVED AND REPLACED MED EXTERNAL DOOR HANDLE. OPS CHECKS GOOD, IAW PH300 MM 52-11-24.
UPPER RUDDER FIXED MASS BALANCE WEIGHT AND FOUND CORROSION. RUDDER ADJUSTABLE BALANCE WEIGHTS AND FOUND THEM TO HAVE CORROSION
CORROSION ON 1 EA RH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS PN#PE915109-L33: CORROSION ON 1 EA LH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS PN#PE915109-L33
TEMP CONTROL BOTH MODES INOP - AT FL410 DUCT 1 OVERTEMP CAS ILLUMINATED. FOLLOWED THE QRH PROCEDURE. IT DID NOT EXTINGUISH. WE WERE AT THE QRH STEP TO TURN BLEED 1 SWITCH OFF WHEN DUCT 2 OVERTEMP CAS ILLUMINATED. WE CHANGED GEARS AND BEGAN THE DUAL DUCT OVERTEMPRATURE QRH. THE QRH PROCEDURE WAS FOLLOWED TO THE END. WE DIVERTED TO IAD AND LANDED.// SIGNOFF// IREMOVED AND REPLACED TEMPERATURE CONTROLLER, OPS CHECKS GOOD .. WORK DONE IAW EMB-1505 AMM 21-61-01. REMOVED AND REPLACED RAM AIR VALVE ASSEMBLY, OPS CHECKS GOOD REF IEMB505 AMM 21-23-03. REPLACED GROUND COOLING FAN JAW EMB505 MM CH 21-23-05.DURING OPSTHECK FAN DID NOT OPERATE.C/W FIM TASK 21-23-00-810-802-A. AND FOUND NO POWER OR GND ON CONNECTOR P0959. VERIFIED POWER AT CB 0345 ON RPDU AND HAD 28V. CYCLED CB AND !RECONNECTED CONNECTOR P0959 AND CONNECTOR P149L AND PERFORMED OPERATLON CHECK AGAIN OPS CHECKS GOOD.
BRAKES SPONGY BOTH PEDALS, BOTH SIDES. BLEED LT AND RT BRAKE SYS IAW MM 32-40-00. OPS CHECKED SATISFACTORY.
LT FUEL FLOW FLUCTUATION DURING CLIMB AND CRUISE FOLLOWED BY LT GEN FAILURE, FOLLOWED BY LT ENGINE VIBRATION SUB: FOUND LT START GEN EXHAUST DUCT HAS LARGE AMOUNT OF SOOT. REMOVED AND REPLACED LT START GEN. C/W SATISFACTORY, OPS CHECK AND PARALLEL IAW MM 24-10-00.
LT FUEL FLOW FLUCTUATION DURING CLIMB AND CRUISE FOLLOWED BY LT ENG FAILURE, FOLLOWED BY LT ENGINE VIBRATION.
THE AIRCRAFT HAS AN AGGRESSIVE ROLL LEFT WITH THE ASSOCIATED TRIM TAB CENTERED. PLACED A YOKE LEVEL ON THE YOKES AND OPENED THE AFT CABIN FLOOR. INSERTED A RIG PIN IN THE AILERON SECTOR. PLACED THE AILERON TRIM TO NEUTRAL. FOUND THE RT AILERON ABOVE STREAM LINE OF WING AND TRIM TAB BELOW STREAMLINE OF AILERON. ADJUSTED THE RT AILERON WING CABLES TO STREAMLINE AILERON TO WING. LT AILERON CHECKS GOOD. TENSION AND TRAVEL CHECKS GOOD ON AILERONS. ADJUSTED TRIM TAB ACTUATOR TO STREAMLINE TRIM TAB TO AILERON. TRAVEL CHECKS GOOD. WITH YOKES LEVEL AND TRIM CENTERED. AILERONS AND TRIM TAB ARE STREAMLINED WITH THE WING. REMOVED RIG PIN. CLOSED AFT CABIN FLOOR IAW MM 27-11-00.
AUTOPILOT MALFUNCTION - LEVEL AT 41000 MSL, THE AUTOPILOT AGGRESSIVELY PITCHED UP TO OVER 1000 FPM. THE AUTOPILOT WAS DISCONNECTED. AFTER 1 MINUTE, THE AUTOPILOT WAS RECONNECTED AND PROBLEM REOCURRED. REMOVED FAULTY LT SIDE PITOT STATIC PORT HOSE AND NR 1 VERTICAL GYRO (FAULTY) INSTALLED NEW HOSE AND REPAIRED VG. PERFORMED PITOT STATIC SYSTEM LEAK TEST GOOD. PERFORMED OPERATIONAL CHECK GOOD
DESCENDING THROUGH 11,000 FT, RT ENGINE LOW FUEL PRESSURE ANNUNCIATOR ILLUMINATED, TRIGGERING RT FUEL BOOST ANNUNCIATOR TO ILLUMINATE. RAN THE ABNORMAL CHECKLIST AND LANDED. NO ENGINE FLUCTUATIONS OR OTHER ENGINE INDICATIONS WERE NOTED. [SUP 4-19-07] SUMPED RT WING TANKS. REMOVED ENGINE FUEL FILTER AND INSTALLED A NEW FILTER. INSTALLED COWL. REMOVED RT ENGINE FUEL LOW PRESSURE SWITCH AND INSTALLED A NEW SWITCH. ALL LEAK AND OPS CHECKS GOOD. ALL WORK DONE IAW CHAPTER 73-30-02 OF THE 560 MM.
LT BRAKE ON RT SIDE TRAVELS ALMOST TO FLOOR DURING BRAKE APPLICATIONS. REMOVED CO-PILOTS IB AND OB BRAKE MASTER CYLINDERS AND INSTALLED NEW MASTER CYLINDERS IAW C560 MM 32-42-02. BLED BRAKES AS REQUIRED.
SHARP IRRITATING ODOR/SMELL MAINLY IN COCKPIT, STRONGER RIGHT AFTER TAKE OFF REMAINED THROUGH WHOLE FLIGHT INCREASED AGAIN DURING DESCENT. RAN ENGINES FOR 30 MINUTES AT 70% FOUND NO ODOR. CHECK OIL LEVELS GOOD. NO SIGN OF EXTERNAL OIL LEAKS. CHECK ACM OIL LEVEL FULL. NO FLUID IN ACM EPA CAN EXAMINED ACM FOR OIL LEAKS NONE FOUND. CHECKED BLEED AIR LINE GOING TO ACM NO SIGNS OF OIL FOUND. REPLACED COLISER SOCK WITH NEW. RAN ENGINES AT 80% FOR 15 MINUTES NO ODOR NOTICED. ENGINE OIL LEVELS STAYED CONSTENT IAW CE560 MM 21-70-00, 71-00-00, 21-21-06
RIGHT SEAT LEFT BRAKE REQUIRES MORE PRESSURE FOR RESPONSIVENESS COMPAIRED TO RIGHT SEAT RIGHT BRAKE. SERVICED AND BLED BRAKE SYSTEM IAW CESSNA 560 MM CH. 32-42-00
DURING TAXI WHEN MAKING A SHARP LEFT TURN, FULL DEFLECTION OF RUDDER PEDALS, F/O'S LEFT BRAKE PEDAL WOULD BECOME STIFF AND ROLL FORWARD, UPON STRAIGHTENING NOSE GEAR BRAKES RETURNED TO NORMAL, ONLY ON F/O SIDE, ONLY DURING LEFT TURN. M2B - T/S TO LOWER HOSE ON CO-PILOTS LT MASTER CYLINDER HITTING RUDDER TORQUE TUBE AND KINKING OVER STOPPING FLUID TO BRAKES. REMOVED & REPLACED LOWER HOSE AND REALIGNED FITTINGS FOR CLEARANCE OF TORQUE TUBE. INSP ALL MASTER CYL & HOSES FOR CLEARANCE AND CONDITION. ALL CHECKS GOOD. BLEED BRAKES C/W TAXI CHECKS. SYSTEM OP'S CHECKS SATISFACTORY AT THIS TIME. ALL WORK DONE IAW CE 560 M/M 32-40-00.
WHEN LEFT RUDDER PEDAL IS PUSHED TO THE FLOOR AND THEN LT BRAKE IS APPLIED THERE IS NO PRESSURE AND TRAVELED TO THE FLOOR WITH NO BRAKING ACTION. BLED BRAKES AS PER CE560 AMM 32-42-00. BRAKE SYSTEM OPERATED NORMALLY DURING NORMAL BRAKING, AND WITH FULL RUDDER DEFLECTION TO LEFT & RIGHT SIDES. ALL MASTER CYLINDERS LEAK AND OP'S CHECK NORMALLY.
DURING TAXI AIRCRAFT PULLS HARD TO RIGHT WHEN BRAKES ARE APPLIED; POST FLIGHT INSPECTION SHOWS SMALL FLUID LEAK ON FRONT SIDE OF LEFT BRAKE.
BRAKES VERY SOFT, YOU HAVE TO PUSH BRAKE PEDALS A LOT FURTHER THAN NORMAL TO MAKE BRAKES WORK IAW CESSNA 560 MM 32-42-00, PERFORMED BRAKE BLEEDING MAINTENANCE PROCEDURE. FOUND LARGE AMOUNTS OF AIR IN SYSTEM ALONG W/ LOW BRAKE FLUID LEVEL. REMOVED AIR AND REPLENISHED BRAKE FLUID DURING BRAKE BLEED PROCESS. OP'S CHECK GOOD, PEDALS TIGHT.
DID NOT GET FULL PWR ON RIGHT HAND ENGINE DURING STATIC TAKEOFF, N1 75.9 ITT 450, N2 83 WITH THROTTLES FULL FWD. REMOVED AND REPLACED RIGHT ENGINE FCU AND FUEL PUMP. ENGINE OPERATES NORMAL AT THIS TIME IAW PWA M/M 71-00-00.
PILOTS LEFT BRAKE ALMOST GOES TO THE FLOOR. ITEM IS UNDER INVESTIGATION.
CAPT LEFT BRAKE PEDAL INTERMITTENTLY LOSES PRESSURE IN TURNS. REMOVED AND REPLACED LT ANTI SKID TRANSDUCER IAW CE 560 MM 32-42-07.
COPILOT'S BRAKE PEDALS ARE SOFT. ITEM IS UNDER INVESTIGATION.
UPON INSPECTION OF WING DEICE BOOTS, THE AERODYNAMIC FILLER WAS DETERMINED TO BE SEPARATING FROM SKIN CAUSING THE DEICE BOOT TO DEBOND. THE DEICE BOOT WAS REMOVED AND SKIN CLEANED OF DEFECTION FILLER. AT THIS TIME, THE SKIN WAS FOUND TO BE CORRODED AT THE LOWER INBOARD SECTION. LEFT WING CORROSION VARIED BETWEEN PITS .005 INCH AND .041 INCH DEEP RIGHT WING SKIN PITS RANGED FROM .002 INCH TO .008 INCHE DEEP. (X)
UPON INSPECTION OF WING DEICE BOOTS, THE AERODYNAMIC FILLER WAS DETERMINED TO BE SEPARATING FROM SKIN CAUSING THE DEICE BOOT TO DEBOND. THE DEICE BOOT WAS REMOVED AND SKIN CLEANED OF DEFECTION FILLER. AT THIS TIME, THE SKIN WAS FOUND TO BE CORRODED AT THE LOWER INBOARD SECTION. LEFT WING CORROSION VARIED BETWEEN PITS .005 INCH AND .041 INCH DEEP RIGHT WING SKIN PITS RANGED FROM .002 INCH TO .008 INCH DEEP. (X)
WHILE INSPECTING LANDING GEAR ASSY DETERMINED BOTH MAIN LANDING GEAR SQUAT SWITCHES MISSING JAM NUT THAT SECURES THE ROD END TO THE TORQUE LINK. THE SQUAT SWITCH ASSY COULD BE TURNED AND MOVED.